Unknown

Abstract

The invention relates to a guide vane for a gas turbine, comprising an airfoil, a platform arranged at a radial end of the airfoil, an upstream flange extending radially from the platform, and a downstream flange extending radially from the platform, wherein the flanges, together with a section of the platform lying between the flanges, bound a groove extending in the circumferential direction of the gas turbine for the arrangement of a damping element. A surface of the section of the platform bounding the groove is arched radially at least in regions thereof in the direction of an opening of the groove. The invention further relates to a guide vane cluster, a housing for a gas turbine, as well as to a gas turbine.

1 . A guide vane for a gas turbine, comprising an airfoil:
 a platform arranged at a radial end of the airfoil,   an upstream flange extending radially from the platform, and   a downstream flange extending radially from the platform,   wherein the flanges, together with a section of the platform lying between the flanges, bound a groove extending in the circumferential direction of the gas turbine for the arrangement of a damping element,   wherein a surface of the section of the platform bounding the groove is arched radially at least in regions thereof in the direction of an opening of the groove.   
     
     
         2 . The guide vane according to  claim 1 , wherein a surface of the platform facing away from the groove is arched radially at least in regions thereof in the direction of the opening of the groove and/or in that, in cross section, the section of the platform has an at least essentially uniform wall thickness. 
     
     
         3 . The guide vane according to  claim 1 , wherein the airfoil has an exposed vane tip with respect to the platform. 
     
     
         4 . The guide vane according to  claim 1 , wherein the upstream flange has a downstream overhang in the groove, and/or in that the downstream flange comprises an upstream overhang in the groove, and/or in that the upstream flange has an upstream overhang, which, together with the platform, forms a further groove extending in the circumferential direction of the gas turbine, and/or the downstream flange has a downstream overhang, which, together with the platform, forms a further groove extending in the circumferential direction of the gas turbine. 
     
     
         5 . A guide vane cluster for a gas turbine, in which at least two guide vanes according to  claim 1 , are connected to one another by way of at least one common platform for the radial bounding of a flow channel of the gas turbine. 
     
     
         6 . A housing for a gas turbine, with a flow channel, comprising:
 a plurality of guide vanes each including:
 a platform arranged at a radial end of the airfoil, 
 an upstream flange extending radially from the platform, and 
 a downstream flange extending radially from the platform, 
 wherein the flanges, together with a section of the platform lying between the flange, bound a groove extending in the circumferential direction of the gas turbine for the arrangement of a damping element, 
 wherein a surface of the section of the platform bounding the groove is arched radially at least in regions thereof in the direction of an opening of the groove; 
   and/or a plurality of guide vane clusters each including:
 at least two of the guide vanes connected to one another by way of at least one common platform for the radial bounding of a flow channel of the gas turbine; 
   are arranged in a cascade manner, wherein the grooves of the guide vanes and/or the guide vane clusters extending in the circumferential direction of the gas turbine are aligned flush with one another, and wherein at least one damping element is arranged in at least one of the grooves.   
     
     
         7 . The housing according to  claim 6 , wherein the at least one damping element has a recess in the region of the section of the associated platform arched radially in the direction of an opening of the groove, and/or, in cross section, the damping element is U-shaped or O-shaped or clamp-shaped in design, and/or the damping element is configured and arranged to be linear in the circumferential direction. 
     
     
         8 . The housing according to  claim 6 , wherein, in cross section, the damping element has at least three contact points in the groove, and/or the damping element has at least two contact points with the housing. 
     
     
         9 . The housing according to  claim 6 , wherein the damping element is arranged in a bridging manner between at least two mutually adjacent guide vanes and/or guide vane clusters. 
     
     
         10 . An aircraft engine with at least one guide vane according to  claim 1 . 
     
     
         11 . An aircraft engine with at least one guide vane cluster according to  claim 5 . 
     
     
         12 . An aircraft engine with at least a housing according to  claim 6 .